In a recent paper, Bowers and Salpeter described a method for calculating the correlation energy of a classical one-component electron gas. The same problem has been considered by Meeron, Friedman, and Abe, using methods involving the summation of cert infinite classes of diagrams. While the relation between these theories and that of Bowers and Saltpeter is not year clear, it is interesting to note that Abe obtained an equivalent expression by approximating an integral. We have calculated the contribution to the equation of state using Abe's original expression and we found that the equation is valid only for certain values and it gives a correction of the wrong sign. On the other hand, our results are comparable to those which Bowers and Salpeter obtain from higher approximations.

The kinetic energies of pions from radioactive decays in propane have been determined by using the information given by the angles of the secondary particles. This method is independent of any range-energy relation.

The oscillator of the 88-in. cyclotron which is being built in Berkeley is tunable from 5.3 to 16.5 Mc. It delivers a maximum c-w power of 300 kw. At the rated doc voltage of 75 kv the resonator stores 4.5 joules of electrical energy. The transients produced by this amount of energy, during sparking, place unusual requirements upon the design of the oscillator tube. The features of the RCA 6949 which make it particularly well-suited to this type of application are discussed in this paper. Other topics covered are the oscillator anode power supply, the hard-tube modulator, protective equipment, and oscillator instrumentation.

A preliminary investigation of four types of multiplier phototubes under conditions simulating their use in scintillation and Cerenkov nuclear detectors is described. The investigation involves time-spread and rise-time measurements at different reference points on the outpost pulses, as well as observations of some special characteristics of these tubes.

The 9-ANGIE, one of a series of reactor neutronic programs for an IBM 709 or 7090 data processing system, solves the time-dependent, multi-group, neutron diffusion equation for one to eighteen energy groups applied to a rectangular mesh superimposed on either an x-y or an r-z plane. It is characterized by its generalities in region description, boundary conditions, etc., without sacrificing simplicity of input preparation and ease of machine operation. The notation, the style, and the format have been held as consistent as possible with 9-ZOOM, the companion one-dimensional program.

This paper for the Project Vela Technical Symposium is intended to be a brief resume of the principle results of the Cowboy program. The material is taken from a report entitled "Use of Large Cavities to Reduce Seismic Waves from Underground Explosions" by Herbat, Werth, and Spring (1960). As a result, no effect is made to justify each step in the analysis; reference should be made to the complete report.

Previous studies have been made of the relationship among acceleration, specific power, payload fraction, and travel time for many interplanetary missions. These utilized tangential thrust and correspond to the high thrust Hohmann transfer orbits. In addition, a complete optimization of the one way Mars mission has been accomplished. Since the minimum Jupiter round trip time was six and a half years for tangential thrust, calculations were carried out using higher energy transfer orbits. It is shown that the orbit-matching problem cannot be solved with tangential thrust programming in this case. The initial period of acceleration away from the earth's orbit was accomplished using tangential thrust in order to minimize energy expenditure. This was followed by a period of coasting until the proper moment arrived for commencing the orbit-matching maneuver. This terminates when the velocity and spatial coordinates of Jupiter's orbit are matched. The technique used for accomplishing these various orbit matching conditions without iteration are described. Best results for the final maneuver were obtained with the thrust vector approximately normal to the velocity vector. By this technique it is shown that the round-trip Jupiter mission may be carried out in four and an half years with 16% payload and 0.10 …